UAA RocketryPDR Presentation

NASA Student Launch 2014-2015

Launch Vehicle

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Vehicle Dimensions● Overall Length 77.7 inches● Body tube diameter 4 inches

and 0.0625 inch thickness

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Vehicle Materials

● 4 inch 5:1 VonKarmen Filament wound nose cone

● Filament wound ProFusion body and coupler tubing

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Vehicle Materials● Fins and centering rings cut

from 0.1875 inch structural fiberglass

● Motor tube made from wound G12 fiberglass tubing

● Bulkheads and payload compartment CNC cut from 0.125 inch structural fiberglass

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Vehicle Materials

● ¼”-20 stainless steel full threaded rods

● Grade-8 ¼ ”-20 Nylon-insert flanged locknuts

● 0.25 inch foged steel Eyebolts

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Vehicle Materials

● Epoxieso West System 105 Epoxy Resino Henkel Loctiteo JB Weld

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Vehicle Justifications

● Conventional configuration: Nose cone/Payload Compartment, Central Section, and Booster Section

● Aft Nose Cone/Payload section serves as payload ejection mechanism● Dual deployment; drogue and payload ejections simultaneous to

simplify design

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Safety Testing Plans

● AGSE components will be constructed with ample time left to thoroughly test system safety, effectiveness, and consistency

● Extensive ground testing performed to ensure ejection charges perform deployment operations safely and consistently

● Subscale and full-scale launch vehicles will be test launched early and often at Alaska Northstar (NAR) launch events

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Motor Selection

Preliminary Motor Selection:

Aero Tech J415W54 mm Diameter326 mm Length

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Justification for Selected Motor

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Stability Analysis

● Center of Pressure: 59.28 inches from nose● Center of Gravity: 51.42 inches from nose● Static Stability Margin: 1.95● Thrust-to-Weight Ratio: 5.5:1● Rail Exit Velocity: 33.4 feet/second

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Test Plan Overview

● AGSE components to be constructed and tested at UAA Design Studio● Ejection Charges to be tested outdoors adjacent to Design Studio● Subscale and full scale launch events at Lake Louise and Big Lake

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Launch Pad Drawing

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Launch Pad Discussion

● Launch rail is 8020-1530 Aluminum extrusion 180 inches in length● Feet are adjustable to level the apparatus● Declination of launch rail is calibrated to 5 degrees from vertical● Blast pad safely deflects exhaust gases away from grass

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Motor Compartment Dimensions/Discussion● 54 millimeters in diameter and 13 inches in length to accommodate J

sized motor● Motor compartment is G12 wound fiberglass made by ProLine

Rocketry Inc. ● Compartment is bonded to centering rings using JB Weld

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Drouge Parachute System Drawing

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Drogue Parachute Discussion

● Located between booster and central sections● Parachute is a 2 foot Rocketman Parachute● Tethered to rocket with ¼” Aramid rope

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Deployment System Drawing

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Deployment System Discussion

● Entire aft section will deploy simultaneously with main chute at 1000 feet AGL

● Aft section will descend under a 3 foot Rocketman Parachute

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Payload Compartment Drawing

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Payload Compartment Discussion

● Payload compartment is CNC cut from 0.125” structural fiberglass, bonded with West Systems Epoxy

● Hatch is actuated by two servos at opposite ends of the compartment● Over-center geometry of hatch respective to servo motor prevents

hatch from opening

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Main Parachute/Shock Cord Compartment Drawing

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Main Chute Discussion

● The main chute will deploy at 1000 feet AGL● Chute is a 60 inch Iris Ultra Parachute made by Fruit

Chutes● Parachute is sized to allow central and booster

sections to descend with kinetic energy ≤ 75 ft-lbf● Chutes and rocket sections tethered with ¼ inch

Aramid Rope

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Recovery System Drawing

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Recovery System Discussion

● First ejection charge at apogee; booster section and central section separate to deploy drogue chute

● Second and third ejection charges at 1000 feet AGL:o Aft nose cone/payload section descend separately o Central and booster sections descend under drogue chute and main chute

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Nose Cone Drawing/Discussion

Image credit to performancehobbies.com [1]

● 4 inch 5:1 Von Karmen Filament Wound Nose Cone

● Connected to payload compartment

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Tail Fin Drawing/Discussion

● Fins cut from 0.1875 inch structural fiberglass

● Delta-style shape● Dimensions:

o 12 inch root cord o 8 inch tip cord o 5 inch heighto 2 inch sweep length

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AGSE Overview• Control

– Spatial Constraints– Degrees of Freedom – Precision and accuracy

• Components – Base Structure– Arm– End Effector

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Base Structure

• Control Overview– Spatial Constraints

• Retain rocket during payload insertion

– fixed dimensional relationship

– Precision and accuracy• Primary mounting point

for the arm structure

• Contains all electronics and power systems 29

Arm• Control Overview

– Spatial Constraints• Of sufficient height to

remain clear of Launch Vehicle

– 1 degrees of freedom• Boom: Rotation – Yaw

– Precision and accuracy • Position

switches/sensors30

Linear Motion System• Control

– Spatial Constraints• Of sufficient length to

clear the base station• Of sufficient length to

reach the ground– 1 Degree of Freedom

• LMS: Translation - Heave– Precision and accuracy

• Ground sensing capability 31

End Effector• Control

– Spatial Constraints• Of sufficient width to

capture a 6” area – Precision and accuracy

• Closing pressure detection

• Orientation of capture

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AGSE Integration and Testing• 3D component models• Assembly checks – QC• Iterative testing at subsystem and system

levels • Sensor/program testing de-bugging

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References

[1]https://www.performancehobbies.com/secure/store.aspx?groupid= 31820148555848

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